Aeronautical wheel



April R. J. MOLAUGHLIN 2,280,715

AERONAUTIGAL WHEEL Filed Oct. 4, 1940 Patented Apr. 21, 1942 UNITEDSTATES PATENT OFFICE AERONAUTICAL WHEEL I 7 Robert J. McLaughlin,Brooklyn, N. Y.

Application October 4, 1940, Serial No. 359,801

'7 Claims.

My invention relates to improvements in lifting devices for airships, inwhich two currents of air are driven together by screw propellers, andcompressed inside a fixed, semicircular drum, so that they reactupwardly on the drum, and escape downwardly through turbine vanes into avortex maintained around the drum by a series of revolving fans. Thissteady supply of air fills the rarefied zone and destroys the downwardsuction of the lower part of the vortex so that the rarefied zone in theupper part of the wheel remains unchanged and causes a heavy suction tobe felt at the upper part of the machine on the principle of thecyclone. This unbalanced lift raises the airship with terrific force andenables it to move in the rarefied region high above the earth.

The objects of my invention are first, to provide a new and improvedaeronautical wheel of greater efiiciency, and to furnish a novel andingenious fixed inner wheel with the strength necessary to bear theterrific cyclonic strains which will be felt by the central zone of therotor; second, to supply a semicircular drum and a circular vacuumtrough, in the lower part of which is placed a series of fixed turbinevanes; third, to install an axial torsion drum to stiffen the fixed axisof the machine; fourth, to devise annular tires for both wheels; fifth,to provide an axial clamp to govern the position of the innor wheel andthe direction of its pull; and sixth, to supply a handle to turn theaxis shaft of the inner wheel.

I attain the objects of my improvement by the mechanism shown drawing,in which Fig. l is a vertical section of the machine, with some parts inelevation;

Fig. 2 is a side elevational view, in which some parts are broken awayto more clearly show others;

Fig. 3 is an enlarged detail view, similar to part of Fig.

in the accompanying Fig. 4 is a fragmental top plan view of the tosimilar parts 2,035,176, which discloses a certain revolvable a wheel,and a feature of the instant case resides in compound tire or rimstructure for an improved revolvable wheel.

Referring in detail to the drawing, a rim I of said wheel includes onone lateral side, an inner circular plate H), of sheet metal, such asaluminum, and an outer circular plate 50, while on the opposite side ofthe wheel the structure includes a rim 2 having an outer circular plate5| and an inner plate 53.

Rigidly connecting the inner plates Ill, 53 of the respective rims is aseries of cross sectionally vanes or blades 3, the opposite ends of theblades being permanently metallically attached to said plates. Theplates [0, 50 of the rim l are braced by interposed rings or bands 9,54, and bracing the, plates 51, 53 of the rim 2 are two rings 55, 56.

Additional stiffening means for the wheel rims include (see also Fig. 3)ring bands 8, 51, the latter being between the plates 5|, 53, and twobands 59, 60, between the plates 19, 59. The respective bands 8, 5i, and59, (iii, with the circular plates, as 5|, 53, form tubes, and thesetub-es rigid- :fy the rim structures at the leading edges 58 of theblades 3, which blades are themselves tubular, it being seen that theinnermost bands 57, 69 are aligned with said edges.

Two oppositel pitched propellers 5, 6, of the device or propulsionmeans, find supports on standards 3!, 32, which may be mounted on anaircraft or bod to be moved. as propulsion means therefor, saidpropellers being unitary with the aforesaid rims l, 2, as hereindisclosed.

Formed with the hub of the propeller 6, and revolvable in a bearing 35on the standard 32, is a stub shaft, as shown, and cooperating with thestub shaft is a usual engine 35, a fragment of which is shown, forrevolving the propellers 5, 6, as a unit, with their transverselydisposed blades 3.

In the hub of the propeller 6 is a socket 33, in which is looselydisposed one end 34 of an ordinarily fixed, selectively turnable orrevolvable shaft 4, and on this shaft, at the hub of the propeller 5, isa bearing 44, The shaft 4, which is revolvable when predetermined, as bya handle 42, finds a bearing at 4| in a hub 40 of the standard orsupport 31, and means for ordinarily preventing rotation of the shaft 4include a clamping device 39 having a handle 43.

The shaft 4 serves a double purpose, as Where at 44, the propeller 5 isjournalled thereon. On the annular central line of the respective rings,

as 55, 56, 8, 51, are four groups of radially disposed apertures 62,each substantially like the others, and best seen in Fig. 3. Also alikeare four extensions 1 of the blades of the propeller 5, and four similarextensions of the propeller blades 6.

According to one method of assembling the elements of the outer wheelmember, the ring bands 55, 56, 8, 51, are placed between the circularplates, as 51, 53, for fixation, and then the extensions are placed inthe apertures 62. In this part of the assembly, as on one side, thebands 55, 56 may first be attached to the plate 53, and the bands 8, 51to the plate 5!, following which said plates with their attachments arefitted together. Subsequent to insertion of an inner annular frame, aspresently described, the extensions I, even before being metallicallysealed, exert a holding function. The outer ends of the blades of thepropellers 5, 5 are fixedly attached 1 to the innermost ends of theextensions 1.

Fast on the shaft 4 is a drum 3d, the latter having annular flanges 31,33, which are attached as by fastening elements, not shown, to saidshaft. Fixedly mounted on the drum 3!], at one end thereof, are theinner ends of four like spokes 28, and fast with the opposite end ofsaid drum are four like spokes 29. The outer ends of the spokes 23 haverigid therewith a circular plate M, and fixed on the outer ends of thespokes 28 is a circular plate 63.

The shaft 4 and its mountings including said spokes and the plates 14,63 form an annular frame or wheel, and connecting said plates at theinner edges of semi-circular portions thereof in a partition orsemi-cylindrical part 38 of a drum frame. The drum frame segment 38includes transverse rods it, the ends of which are rigid with the platesM, 63 thereat. Covering the rods [3 at their innermost sides is asheeting I? of metal, such as aluminum, and sealingly covering said rodson their outer sides is a sheeting I 3, thereby forming a chamber ortrough IS.

The innermost circular rim plates of the propulsion means are deeperthan the outer plates, the plate l9 having thereon an annular flange H,which is of less diameter than that of the plate M at its periphery, andthere being a flange St on the plate 53, like the flange l l. Thedrawing herein is slightly exaggerated, for clarity, but the flanges I Iand 64 are substantially close, consistent with freedom of relativemovement, to the outer side margins of the plates I4, 63.

On the outer side of the plate l4, close to the flange I I, is anannular projecting flange l2, and on the plate 33 is an outer annularflange 65. The sides of the chamber I3 are therefore substantiallysealed against inward or outward air movement, and as thesemi-cylindrical frame member 33 terminates as shown in broken lines inFig. 2, transversely of opposite ends of spokes 28, 29, the ends of thechamber l3, except for bafiles or turbine blades i8, 25, 2|, 22, 23, 2d,25, 26, 21, are therefore open.

Opposite the partition 38 and also rigid at their opposite ends with theplates I4, 63, are the blades l82l, and as the inner frame may be turnedinto a selected position, the member 33 ma be directed upwardly, asshown in the drawing, whereby to cause vertical lift, or the partitionmay be directed forwardly, as for use on an aircraft for horizontalflight.

The advantages of obtaining a negative air ill) pressure by creatingcentrifugally acting air currents, as in the present case, and asreferred to in the general statement hereof, together with the statementof my aforesaid patent, are well known. Other issued patents discussthese advantages and principles, even the experiments of M. Eiffel beingcited in the disclosures of some of them, as proof. But the instantdisclosure differs from the prior art, especially as recited in theclaims which are appended hereto.

As the present blades 3, during revolution of the outer propulsionframe, with its stub shaft at 35, pass around and outside of the arcuateframe member 38, air is evacuated from the chamber I 3, thereby causinga negative pressure,

which tends to draw the member 38 thereto, that is, forwardly, with anattached machine or aircraft. The blades 3, owing to their crosssectional shape, their pitch, their distance from the transverse axis ofthe device, and from the stationary drum 38, as well as the terminalincorporation of these blades in the rim elements, differ materiallyfrom the apparently corresponding parts of my issued patent. Othercomparative difference and advantages exist in the present case, asbecause of the inner stationary annular wheel or frame, which is part ofthe structure involved in securing the stated objects of the invention.

The propeller blades 5, 5, which provide an enclosure therebetween, areof considerable length, relative to the edge to edge dimensions of theblades 3, and therefore the positive air pressure within the enclosure,differing from usual atmospheric pressure, and against the inner surfaceof the member 38, as caused by the inwardly directed air streams of thepropeller blades 5, 5, is greatly augmented.

It is a feature of the arcuate group of stationary blades l52'l that oneend thereof is near the otherwise open end of the chamber I3 thereat,and the opposite end of said group, being the member 21, is near theother end of the same chamber 13.

The drum 39 is an advantage, as owing to its diameter, opposite theportions of the propellers 5, 5 which may have little or no aerodynamicefficiency, and while air pressure against the surface H is increased,as herein indicated, the compressed air opposite said surface findsavenues of escape through the spaces between the controlling bladesl9-2l, and also between the respective blades 3, as the latter pass theblades 19-21. On viewing Fig. 2, it is seen that the air stream, fromthe inner compressed region, opposite said surface 11, and past therelatively large drum 3i], is first directed largely against the concavesurfaces of the blades Iii-21. It is noted that there may be no director radial path for this air stream (see the arrow 13) past said group,and therefore there is no direct path for said stream to follow, wherebyit might directly, radially strike the leading edges of the blades 3.

Air deflected from the concave sides of the blades ill-21 travelsagainst the concave sides of the blades 3. These latter blades rotatefrom left to right (Fig. 2). Therefore, air striking the concave sidesof said blades 3 tends to urge them in the direction of rotation. Thisbecomes apparent from viewing the direction of air movement indicated bthe arrow it! against a blade 21, and from thence, referring to thearrow H, against a blade 3. This blade 3 is shown in only one of severalor continuous positions, but on viewing another position l3, in dot anddash lines, of a blade 3, as soon as an air stream, as from a blade 23,urges a blade 3 past the next blade 24, then a stream from the blade 24will immediately strike the concave side of the same blade 3 (being thesecond position 73) when the latter just passes said blade 24.

I claim:

1. A propulsion means comprising an outer revolvable annular framehaving spaced sides including rims, supports for said frame, a fixedaxis, oppositely pitched propellers forming parts of said sides andjournaled on the supports and axis, said propellers, providing anannular enclosure therebetween, transverse blades connecting said rims;an inner frame rigid with said axis, and having spaced annular rimplates near said rims, a semi-cylindrical partition connecting portionsof said plates and providing a chamber between the path of the bladesand one side of said enclosure, and bafile blades connecting said plateson the opposite side of said enclosure.

2. A propulsion means for propelling a body through a fiuid, comprisingin combination an outer revolvable annular frame having spaced sidesincluding rims, supports for said frame, a fixed axis, oppositelypitched propellers forming parts of said sides and journaled on thesupports and axis, a drive shaft rigid with one of said propellers,transverse blades connecting said rims; an inner frame rigid with saidaxis and having spaced annular rim plates, at semi-cylindrical shellconnecting portions of said plates and providing a chamber between thepath of the blades and the outer surface of said shell, said chamberhaving open ends, and baflle blades connecting opposite portions of saidplates.

3. A propulsion means for an aircraft comprising an outer revolvableframe having spaced sides and including annular rims, transverse bladesconnecting said rims, frame supports, an axis, two propellers disposedin said sides and journaled on the supports and axis, said propellersproviding an enclosure therebetween; a second frame rigid with said axisbetween said sides and having spaced hinge plates near said rims, asemi-cylindrical partition rigid with portions of said plates andproviding at its outer face a vacuum chamber, the chamber being nearsaid blades on one side of the enclosure, said propellers havingoppositely pitched blades to urge air streams into the enclosure, theair being compressed against the inner face of said partition, and meansalso rigid with said plates for controlling escape of the compressed airfrom the opposite side of said enclosure.

4. In an aviation propulsion device having a revolvable frame comprisingtwo sides including annular rims and having therein and providing aninterposed enclosure two oppositely pitched propellers, said rims havingspaced blades therebetween, a fixed frame internally of the first frameand having circular plates near said rims, a partition of segmental drumframe shape carried by said plates and providing a vacuum chamber at itsouter surface near the path of said blades on one side of the enclosure,said propellers adapted to compress air within the enclosure against theinner face of the partition, and means for controlling escape of thecompressed air through the spaces between said blades on the oppositeside of said enclosure.

5. The combination with a propulsion means for aircraft comprising atransverse shaft having a wheel including spaced sides journaledthereon, rims of large diameter forming parts of said sides, oppositelypitched propellers also forming parts of said sides and having theiroutermost portions rigid with said rims, propulsion blades havingcertain pitch and fixedly mounted between said rims; of an inner Wheelrigid with the shaft between said sides and including spaced rim platesof less diameter than said rims, said inner wheel including an axialdrum and having spokes carrying said plates, a semi-circular drum framesegment carried by portions of said plates and forming a vacuum spacenear the path of said blades; said propellers adapted to compress air inthe space inwardly of the segment; and blades carried by oppositeportions of said plates and each having a pitch angle opposite to theangle of said propulsion blades.

6. The combination according to claim 5, in which said propulsion bladesare equally spaced apartaround the circle of the rims, the fixed bladesbeing equally spaced apart around substantially a half circle of saidplates, and said fixed blades being less in number than half of thenumber of said propulsion blades.

7. In a device of the class described having a revolvable framecomprising two sides providing an enclosure and including annular rims,means for forcing air into the enclosure, said means including a screwpropeller, said rims having spaced connecting transverse blades thereon;a fixed frame within the first frame and having circular plates near therims, -a segmental partition carried by the plates on one side of theenclosure and providing a vacuum chamber at its outer surface, the airbeing compressed against the inner face of the partition, and means forcontrolling escape of the compressed air on the opposite side of saidenclosure.

ROBERT J. MCLAUGIEIN.

